着舰导引中的H∞飞行/推力综合控制设计

以提高低动压着舰时动态跟踪及抑制舰尾气流扰动的性能为期望 ,基于线性矩阵不等式 (LMI)的 H∞ 控制理论 ,提出了保持由地速构成的迎角 αd 恒定的 H∞ 飞行 /推力综合控制增广模型结构。使飞机在接近舰尾处于雷达导引系统关闭的关键时刻 ,该系统仍有姿态保持及抑制气流扰动的优良性能 ,从而改变了传统设计需由导引系统纠正气流扰动而引起的轨迹偏离。基于工程应用 ,文中提出了 H∞ 控制器的降阶方法 ,进行了离散化实时仿真验证。仿真表明 ,本文开发的系统能够很好地满足设计要求

FLIGHT/THRUST INTEGRATED CONTROL USING H∞ SYNTHESIS IN AUTOMATIC CARRIER LANDING SYSTEM

The landing task of an aircraft under low aerodyna-mic pressure on carrier requires precise airplane control. A flight/thrust integrated control system (FTICS) with constant αd, actual angle of attack, is developed using LMI-based H∞ synthesis. The typical single input/output specifications are translated into the weighting functions of an H∞ output-feedback synthesis problem. The motivation of the work is to improve the key performance of dynamic tracking and air disturbance attenuation. The FTICS can keep the attitude angle and the path angle unchangeable as the airplane is passing through the ramp at which the tracking radar doesnot work and the guidance signal is terminated. For engineering application, an order-reduction method of the H∞ controller is also proposed. Simulational results indicate that the system satisfies the design requirements quite well.